CN212254182U - Composite pressure-temperature probe - Google Patents
Composite pressure-temperature probe Download PDFInfo
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- CN212254182U CN212254182U CN202021215606.4U CN202021215606U CN212254182U CN 212254182 U CN212254182 U CN 212254182U CN 202021215606 U CN202021215606 U CN 202021215606U CN 212254182 U CN212254182 U CN 212254182U
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Abstract
The utility model provides a compound pressure-temperature probe, contains and sets up in the inside total pressure piezometer pipe of the probe body of rod, a total temperature thermocouple, three near-end static pressure piezometer pipes, one distal end static pressure piezometer pipe and one distal end temperature thermocouple, the probe body of rod contain the horizontal body of rod and the vertical body of rod that mutually perpendicular set up, the front end of the horizontal body of rod passes through the changeover portion and connects the static pressure measurement section, the pressure measurement head is connected to the static pressure measurement section, the end-to-end connection of the vertical body of rod draws forth the section, is provided with the locating piece on the vertical body of rod just to the. The utility model discloses general in measure from low-speed to supersonic speed pneumatic parameters such as total temperature, quiet temperature, total pressure, static pressure, incoming flow mach number, the velocity of flow of air current under the incoming flow condition simultaneously with the ground, can be used for wind-tunnel experiment and aircraft flight parameter's test, measurement accuracy is high, compatible strong, the commonality is good.
Description
Technical Field
The utility model relates to a pressure, temperature and speed test field especially relate to a compound pressure-temperature probe.
Background
The total/static pressure probe is also called as a pitot tube, a speed tube and an airspeed tube in the field of wind tunnel experiments. The measuring principle and the probe structure of the porous pneumatic probe with three holes, five holes, seven holes and the like in the flow field testing technology are developed from a total/static pressure probe, the total/static pressure probe is the basis and the parent body of the porous pneumatic probe technology, is the inspection standard of other flow testing means in the wind tunnel experiment of impeller machinery, and is one of the most main and most convenient measuring tools for calibrating working conditions such as the incoming flow Mach number, the attack angle and the like. The total/static pressure probe is also an important atmospheric data sensor for detecting the total pressure and the static pressure of the surrounding atmospheric environment of the airplane under the flight condition and converting the total pressure and the static pressure into flight parameter information such as flight Mach number, air pressure altitude, lifting speed and the like. Therefore, the total/static pressure probe is a ruler in the field of flow test and is an important prerequisite for ensuring smooth development of wind tunnel experiments and safe flight of aircrafts.
In the prior art, a general total/static pressure probe can only measure the total pressure and the static pressure at a measuring point, and then the speed, the Mach number and the like at the measuring point are obtained through indirect calculation according to a Bernoulli equation. In the high subsonic velocity flow field, the incoming flow is disturbed by the total/static pressure probe to form a disturbed flow field around the probe, however, the static pressure of the airflow measured by the static pressure tube is actually the static pressure in the disturbed flow field of the probe, and the value is higher than the static pressure of the local actual incoming flow, namely the value is called as 'position error', and therefore, a pneumatic compensation measure is needed. In the span and supersonic flow field, the total pressure pipe and the static pressure pipe are located behind a shock wave structure of a probe head area, the total pressure and the static pressure of the subsonic flow after the shock wave are directly measured, the total pressure and the static pressure of the subsonic flow after the shock wave are not the actual total pressure and the static pressure of the span and supersonic flow in the local, conversion needs to be carried out through a Pitot-Rayleigh formula, and therefore the static pressure at the far end needs to be measured at the same time to serve as a known quantity during the conversion. Therefore, in the process from the high subsonic speed to the supersonic speed, the calculation method for measuring the pneumatic parameters by using the total/static pressure probe needs to make a rotation, and how to automatically determine when the rotation needs to be made is a problem which is never answered by the prior art.
In addition, whether the incoming flow total/static pressure probe in the wind tunnel experiment is aligned to the incoming flow direction or not and whether the installation is accurate or not greatly influence the accuracy of the experimental incoming flow Mach number and the attack angle. Similarly, the problem of large measurement error of a pure total/static pressure probe also occurs in the large-attack-angle maneuvering flight of the aircraft, and particularly in the case of icing or dust blockage, the reliability of the total/static pressure probe determines the safety of the aircraft.
The measurement principle of the existing total/static pressure probe is based on the theoretical basis of constant absolute energy isentropic Bernoulli equation, i.e.
Wherein the gas compression coefficient
The dynamic pressure change caused by compressibility of a compressible gas (Mach number Ma > 0.3) is characterized. To solve the incoming flow velocity v, the Mach number of the local air flow is also known
And speed of sound
It is required that the static temperature T of the local air flow must be measured, which undoubtedly increases the useThe difficulty of obtaining hypersonic incoming flow by using the existing porous pneumatic probe and calibration data thereof. Meanwhile, the theory is not suitable for the cross-over and supersonic flow with the adiabatic irreversible unequal entropy of the shock wave structure.
SUMMERY OF THE UTILITY MODEL
The utility model provides a compound pressure-temperature probe is general to measure simultaneously with the ground from low-speed to supersonic speed pneumatic parameters such as total temperature, quiet temperature, total pressure, static pressure, incoming flow mach number, the velocity of flow of air current under the incoming flow condition, can be used for wind-tunnel experiment and aircraft flight parameter's test, and measurement accuracy is high, compatible strong, the commonality is good.
In order to achieve the above object, the present invention provides a composite pressure-temperature probe, comprising: the probe rod body comprises a horizontal rod body and a vertical rod body which are perpendicular to each other, the front end of the horizontal rod body is connected with a static pressure measuring section through a transition section, the static pressure measuring section is connected with a pressure measuring head, the tail end of the vertical rod body is connected with a leading-out section, and a positioning block is arranged on the side wall of the vertical rod body, which is opposite to the incoming flow direction;
the detection ends of the total pressure-measuring pipe and the total temperature thermocouple are arranged at the pressure-measuring head, the detection ends of the three near-end static pressure-measuring pipes are arranged on the side wall of the static pressure measuring section, the detection ends of the one far-end static pressure-measuring pipe and the one far-end temperature thermocouple are arranged on the side wall of the horizontal rod body, and all the pressure-measuring pipes and the thermocouples extend out of the leading-out section.
The molded line of the pressure measuring head is a semiparabolic semi-infinite length rotation body. The expression of the rotation bus of the rotation body is as follows:
wherein the length of the rotation bus of the semiparabolic rotation body is xhLength x of revolution generatrixhAnd a pressure measuring headThe ratio of the outer diameters D of (a) to (b) is referred to as the slenderness ratio f of the probe, and the slenderness ratio f ranges from f to xh3.39-5.82,/D, length x of rotary bushSatisfies x between the total length L from the pressure measuring head to the horizontal rod bodyh/L＝0.1077～0.1538。
The detection end of the total pressure piezometric tube is arranged at the tip of the piezometric head and is opposite to the incoming flow direction, and the ratio D/D of the inner diameter D of the total pressure piezometric tube to the outer diameter D of the probe piezometric head is 0.3-0.5.
The three near-end static pressure measuring tubes comprise a first near-end static pressure measuring tube, a second near-end static pressure measuring tube and a third near-end static pressure measuring tube, and the normal lines of the detecting ends of the three near-end static pressure measuring tubes are consistent with the normal line direction of the outer wall surface of the static pressure measuring section;
the detection end of the first near-end static pressure measuring pipe is arranged on the vertically downward side wall of the static pressure measuring section, and the normal line of the detection end of the first near-end static pressure measuring pipe is parallel to the central line of the vertical rod body; the center of the detection end of the first near-end static pressure piezometric tube is away from the length x of the tip of the probe headsThe following conditions are satisfied:
wherein x ishThe length of a rotary bus of a semi-parabolic semi-infinite length rotating body of the pressure measuring head is d, the inner diameter of the total pressure measuring pipe is d, and the total length from the pressure measuring head to the horizontal rod body is L;
the detection end of the second near-end static pressure-measuring pipe and the detection end of the third near-end static pressure-measuring pipe are arranged on the side wall of the upper half circumference of the static pressure measurement section, the detection end of the second near-end static pressure-measuring pipe and the detection end of the third near-end static pressure-measuring pipe are in axisymmetric distribution, and the symmetry axis is the normal line of the detection end of the first near-end static pressure-measuring pipe.
An included angle between the normal of the detecting end of the second near-end static pressure measuring pipe and the normal of the detecting end of the first near-end static pressure measuring pipe is 120 degrees, and an included angle between the normal of the detecting end of the third near-end static pressure measuring pipe and the normal of the detecting end of the first near-end static pressure measuring pipe is 120 degrees.
The total temperature thermocouple is arranged on the upper side of the total pressure piezometric tube, and the detection end of the total temperature thermocouple is arranged on the piezometric head part through a stagnation cover.
The transition section is a regular rotating body with variable diameter, the diameter of one end of the transition section, which is connected with the static pressure measuring section, is smaller than that of one end of the transition section, which is connected with the horizontal rod body, the length of one end of the transition section, which is connected with the static pressure measuring section, and the tip of the probe head is 3 times of the length of the center of the detecting end of the first near-end static pressure measuring tube from the tip of the probe head, namely 3xsThe length of the transition section is equal to the length x from the center of the detection end of the first near-end static pressure measuring pipe to the tip of the probe heads。
The strand of far-end static pressure-measuring pipe comprises three far-end static pressure-measuring pipe detection ends, and the three far-end static pressure-measuring pipe detection ends are uniformly distributed on the side wall of the horizontal rod body; the strand of far-end temperature thermocouple comprises three far-end temperature thermocouple detection ends, and the three far-end temperature thermocouple detection ends are uniformly distributed on the side wall of the horizontal rod body; the detection end of the far-end static pressure piezometer tube and the detection end of the far-end temperature thermocouple are arranged at intervals; the length from the center of the detection end of the far-end static pressure piezometer tube to the tip of the probe head is xcThe length of the center of the detection end of the remote temperature thermocouple from the tip of the probe head is xcL is the total length of the pressure measuring head to the horizontal rod body, 0.70L.
The normal line of each far-end static pressure measuring pipe detection end is consistent with the normal line direction of the outer wall surface of the horizontal rod body, the included angle between the normal lines of the two adjacent far-end static pressure measuring pipe detection ends is 120 degrees, and one far-end static pressure measuring pipe detection end is arranged on the vertical downward side wall of the horizontal rod body.
Every distal end temperature thermocouple detection end pass through the stagnation cover and set up on the lateral wall of the horizontal body of rod, every distal end temperature thermocouple detection end's normal line unanimous with the normal direction of the outer wall surface of the horizontal body of rod, the contained angle between the normal lines of two adjacent distal end temperature thermocouple detection ends is 120, and one of them distal end temperature thermocouple detection end setting be in the vertical ascending lateral wall of the horizontal body of rod on.
The positioning block is a groove arranged on the vertical rod body, the depth of the positioning block is less than or equal to 30% of the wall thickness of the vertical rod body, and the surface normal direction of the positioning block is opposite to the incoming flow direction.
The total pressure piezometric tube, the first near-end static pressure piezometric tube and the strand of far-end static pressure piezometric tube are linearly arranged on the leading-out section, and the total pressure piezometric tube is arranged in the middle; the total temperature thermocouple and the strand of far-end temperature thermocouple are linearly arranged on the leading-out section; the second near-end static pressure piezometer tube and the third near-end static pressure piezometer tube are linearly arranged on the leading-out section; the total pressure-measuring pipe, the first near-end static pressure-measuring pipe and the strand of far-end static pressure-measuring pipe are arranged in the middle.
Compared with the prior art, the utility model discloses following beneficial effect has:
1. the total temperature thermocouple is embedded between the total pressure measuring pipe of the probe and the inner wall of the pressure measuring head part instead of being bound outside the probe rod body, so that the size of the composite probe rod body is greatly reduced, the composite probe rod body can be maintained on the same size of the traditional pressure probe, and the interference of the composite probe on a flow field is effectively reduced. Meanwhile, a temperature signal measured by the embedded total temperature thermocouple can be used as an important criterion for judging that the head of the incoming flow turbulent flow probe forms a shock wave structure, so that automatic alternation of a subsonic probe calibration algorithm and a supersonic probe calibration algorithm is realized, and the application range of the pneumatic probe is effectively widened.
2. Preferably, the semiparabolic semi-infinite length rotation body is adopted as the molded line of the probe pressure measuring head, the technology is mature, abundant experiments and numerical data support are provided, and the accurate design of the geometric dimensions of each key part of the probe is facilitated. Meanwhile, the influence of the position error of the modern aircraft nose on the probe can be equivalent to the pressure distribution of a semiparabolic semi-infinite length rotation body, so that the pneumatic compensation design scheme of the probe can be simplified.
3. The two static pressure-measuring tubes are adopted to be used as front body pneumatic compensation for static pressure measurement of the direction characteristic pressure-measuring tube and the probe, and meanwhile, the far-end static pressure tube is adopted to be used as rear body pneumatic compensation for static pressure measurement of the probe, so that the position error formed by turbulent probes flowing in the incoming flow under the condition of subsonic velocity incoming flow can be obviously weakened, the influence on the use of the whole probe after the blockage of a single static pressure-measuring tube in the actual use process can be avoided, and the measurement accuracy of the probe is improved.
4. The transition section of the regular rotating body with the variable diameter and the far-end static pressure measuring pipe arranged on the horizontal rod body of the probe can obtain a static pressure value equal to the far-end incoming flow under the conditions of crossing and supersonic incoming flow, so that the accuracy of solving the real total static pressure value under the conditions of crossing and supersonic incoming flow by using a Pitot-Rayleigh formula is improved. In addition, the remote temperature thermocouple can also be used as the pneumatic compensation of the total temperature thermocouple of the probe pressure measuring head, and the reliability of the temperature change as the criterion for generating shock waves is improved.
5. Whether the probe installed in the wind tunnel experiment is over against the incoming flow direction or not can be judged by adopting two pressure differences obtained by measuring through the direction characteristic pressure measuring pipe, the accuracy of probe installation centering is improved, and therefore the accuracy of experiment incoming flow Mach number and attack angle is effectively improved. Meanwhile, under the condition of icing or dust blockage, the problem of large total and static pressure measurement errors is reduced, and the reliability and safety of the aircraft are improved.
Drawings
Fig. 1 is a main structure diagram of a composite pressure-temperature probe according to the present invention.
Fig. 2 is a flow direction cross-sectional view of a main structure of a composite pressure-temperature probe provided by the present invention.
Fig. 3A-3B are a flow direction sectional view and a deployment direction sectional view of a pressure measuring head structure of a composite pressure-temperature probe according to the present invention.
Fig. 4A to 4C are a flow direction sectional view, a spread direction sectional view and a three-way structure view of a probe horizontal rod structure of the composite pressure-temperature probe provided by the present invention.
Fig. 5 is a cross-sectional view of the positioning block structure of the composite pressure-temperature probe according to the present invention.
Fig. 6A to 6B are a structural layout and a top view of a lead-out section of a composite pressure-temperature probe according to the present invention.
Detailed Description
The following describes a preferred embodiment of the present invention with reference to fig. 1 to 6B.
As shown in fig. 1, the present invention provides a composite pressure-temperature probe, comprising: the pressure-measuring tube is pressed to total pressure 8, a total temperature thermocouple 13, three near-end static pressure-measuring tubes, one distal end static pressure-measuring tube and one distal end temperature thermocouple of setting in the inside probe body of rod, the probe body of rod contain the horizontal body of rod 4 and the vertical body of rod 5 that mutually perpendicular set up, the front end of the horizontal body of rod 4 passes through changeover portion 3 and connects static pressure measurement section 2, pressure measurement head 1 is connected to static pressure measurement section 2, the end-to-end connection of the vertical body of rod 5 draws forth section 7, is provided with locating piece 6 on the vertical body of rod 5 just to the lateral wall of incoming flow direction.
The detection ends of the total pressure-measuring pipe 8 and the total temperature thermocouple 13 are arranged at the pressure-measuring head part 1, the detection ends of the three near-end static pressure-measuring pipes are arranged on the side wall of the static pressure measuring section 2, the detection ends of the one far-end static pressure-measuring pipe and the one far-end temperature thermocouple are arranged on the side wall of the horizontal rod body 4, and all the pressure-measuring pipes and the thermocouples extend out of the leading-out section 7.
The horizontal rod body 4 and the vertical rod body 5 play a role in wrapping all pressure measuring tubes and thermocouples, the structural strength of the whole probe is enhanced, and all the pressure measuring tubes and the thermocouples extending out of the leading-out section 7 can be connected into a digital sensor array pressure testing module (DSA) and a distributed optical fiber temperature sensing system (DTS) through a pneumatic connector.
The total pressure and pressure measuring tube 8, the total temperature thermocouple 13 and three near-end static pressure and pressure measuring tubes close to the probe head sequentially pass through the static pressure measuring section 2, the transition section 3, the horizontal rod body 4 and the vertical rod body 5 and finally extend out of the leading-out section 7. The strand of far-end static pressure-measuring pipe comprises three far-end static pressure-measuring pipes, the strand of far-end temperature thermocouple comprises three far-end temperature thermocouples, and the three far-end static pressure-measuring pipes and the three far-end temperature thermocouples are respectively converged into a strand of pressure-measuring pipe and a strand of thermocouple wire, then sequentially pass through the horizontal rod body 4 and the vertical rod body 5, and finally extend out of the leading-out section 7.
As shown in fig. 2 and fig. 3A, in an embodiment of the present invention, the molded line of the pressure measuring head 1 is preferably a semiparabolic semi-infinite length rotation body, and the rotation generatrix expression of the rotation body is as follows:
wherein the length of the rotation generatrix of the semiparabolic rotation body is recorded as xhAnd the length x of the bushThe ratio of the length to the diameter D of the probe pressure measuring head is called the slenderness ratio of the probe, and is marked as f, and the value range of the slenderness ratio is preferably that f is xh3.39-5.82% of/D; at the same time, the length x of the bushPreferably x is satisfied between the total length L from the pressure measuring head to the horizontal rod bodyh/L＝0.1077～0.1538。
The utility model discloses an embodiment, total pressure-measuring pipe 8's detection end set up the most advanced just incoming flow direction at pressure-measuring head 1, total pressure-measuring pipe 8's internal diameter D and probe pressure-measuring head external diameter D's ratio is called probe pressure-measuring head internal diameter and external diameter ratio, marks as D/D, its value scope is preferably D/D ═ 0.3 ~ 0.5.
In an embodiment of the present invention, because the static pressure measuring end is disposed at the lower side to measure a more accurate static pressure value, the total temperature thermocouple is preferably disposed at the upper side for the purpose of measuring accuracy and mutual noninterference. Preferably, the total temperature thermocouple 13 penetrates through a metal round pipe embedded between the upper side of the total pressure piezometer tube and the inner wall of the probe piezometer head, and the detection end of the total temperature thermocouple is a tangent plane of the round pipe and the outer wall of the probe rod body, so that a conical rectifying stagnation cover 13 is formedz。
As shown in fig. 2 and fig. 3B, in an embodiment of the present invention, the three near-end static pressure-measuring tubes near the probe head include a first near-end static pressure-measuring tube 9, a second near-end static pressure-measuring tube 10 and a third near-end static pressure-measuring tube 11, and the second near-end static pressure-measuring tube 10 and the third near-end static pressure-measuring tube 11 also serve as directional characteristic pressure-measuring tubes.
The detection end of the first near-end static pressure measuring pipe 9 is arranged on the vertical downward side wall of the probe static pressure measuring section 2 (the static pressure measuring end is arranged at the lower side and can measure a more accurate static pressure value), the normal line of the detection end of the first near-end static pressure measuring pipe 9 is consistent with the normal line direction of the outer wall surface of the probe static pressure measuring section 2, and the distance x from the center of the detection end of the first near-end static pressure measuring pipe 9 to the tip of the probe head issThe following conditions are preferably satisfied:
the detection ends of the second near-end static pressure measuring pipe 10 and the third near-end static pressure measuring pipe 11 are arranged on the side wall of the upper semicircle of the static pressure measuring section 2, the second near-end static pressure measuring pipe 10 and the third near-end static pressure measuring pipe 11 are symmetrically distributed by taking the normal of the detection end of the first near-end static pressure measuring pipe 9 as a symmetry axis, preferably, the included angle between the connecting line of the center of the second near-end static pressure measuring pipe 10 and the circle center of the static pressure measuring section 2 and the connecting line of the center of the first near-end static pressure measuring pipe 9 and the circle center of the static pressure measuring section 2 is 120 degrees, and the included angle between the connecting line of the center of the third near-end static pressure measuring pipe 11 and the circle center of the static pressure measuring section 2 and the connecting line of the center of the first near-end static pressure measuring pipe 9 and the circle center of.
As shown in fig. 1, in an example of the present invention, the transition section 3 is a regular rotating body with a variable diameter, and the diameter of the end of the transition section connected to the static pressure measuring section 2 is smaller than the diameter of the end connected to the horizontal rod body 4. The distance between the initial position of the transition section 3 and one end of the static pressure measuring section 2 and the tip of the probe head is preferably the distance between the center of the detecting end of the first near-end static pressure measuring pipe and the tip of the probe head3 times the distance of the ends, i.e. 3 ×)sAnd the length of the transition section is preferably equal to the distance x between the center of the detection end of the first near-end static pressure measuring pipe and the tip of the probe heads。
As shown in fig. 2 and fig. 4A-4B, in an embodiment of the present invention, the three pressure measuring ends 12r, 12l, 12s of the one distal static pressure measuring tube 12 are disposed on the lateral wall of the probe horizontal rod 4, the normal line of each detecting end is consistent with the normal line direction of the probe outer wall surface, the included angle between the connecting line of the center of the pressure measuring tube and the central point of the horizontal rod 4 is preferably 120 °, and one of the pressure measuring ends is located at the vertical downward position of the lateral wall of the probe horizontal rod 4, so that the optimal pressure measuring effect can be obtained.
Three temperature measuring ends 14r, 14l and 14s of the strand of far-end temperature thermocouple 14 are arranged on the side wall of the probe horizontal rod body 4, the normal line of each detecting end is consistent with the normal line direction of the outer wall surface of the probe, the included angle between the connecting line of the center of the temperature measuring end and the central point of the horizontal rod body 4 is preferably 120 degrees, and one temperature measuring end is located at the vertically upward position of the side wall of the probe horizontal rod body. The detecting end of the temperature thermocouple 14 is not directly arranged on the surface of the temperature measuring end, but is additionally provided with a stagnation cover.
On the side wall of the probe horizontal rod body 4, the far-end static pressure piezometer tube and the far-end static temperature thermocouple are alternately arranged at intervals, and the central position of the probing end of the far-end static pressure piezometer tube and the far-end static temperature thermocouple are at a distance x from the tip of the probe head 1c0.70L (as shown in fig. 2).
As shown in fig. 4c, in an embodiment of the present invention, the three far-end static pressure-measuring tubes 12r, 12l, 12s and the three far- end temperature thermocouples 14r, 14l, 14s are respectively assembled into a strand of pressure-measuring tube 12 and a strand of thermocouple wire 14 at the joint of the horizontal rod body 4 and the vertical rod body 5 of the probe, and then sequentially pass through the horizontal rod body 4 and the vertical rod body 5 of the probe, and finally extend out from the lead-out section 7.
As shown in fig. 1 and 5, in an embodiment of the present invention, the vertical rod 5 of the probe is provided with a positioning block 6 facing the incoming flow direction, the positioning block 6 is a rectangular groove milled on the vertical rod 5 of the probe, and the depth of the positioning block 6 is less than 30% of the wall thickness of the vertical rod of the probe in order to ensure that the rigidity of the probe is not affected. The normal direction of the surface of the positioning block 6 is consistent with the direction of the tip of the probe pressure measuring head 1 and is required to be opposite to the incoming flow direction. The determination of the normal direction of the surface of the positioning block 6 is adjusted by the difference value of two air flow pressure values measured by the directional characteristic pressure measuring tube, firstly, the deflection angle of a probe rod body relative to the incoming flow is rotated through a calibration wind tunnel experiment, so that the pressure difference value of a second near-end static pressure measuring tube 10 and a third near-end static pressure measuring tube 11 serving as the directional characteristic pressure measuring tube is zero, at this time, the probe pressure measuring head 1 can be judged to be just opposite to the incoming flow direction, and the normal direction of the surface of the positioning block 6 can be determined. When the composite pressure-temperature probe is installed in the wind tunnel cylinder, the horizontal ruler can be attached to the positioning block 6, the probe rod body is rotated by adjusting the degree of deviation of bubbles on the horizontal ruler from the alignment line of the horizontal ruler, and finally the bubbles of the horizontal ruler are ensured to be located on the alignment line, so that the direction of the head of the probe at the moment is just opposite to the incoming flow direction.
As shown in fig. 6A to 6B, in an embodiment of the present invention, the leading-out section 7 is in a three-row linear symmetrical arrangement, and each pressure measuring tube and thermocouple are led out from the leading-out section 7, and each pressure measuring tube and thermocouple are connected to a pneumatic connector. Specifically, the total pressure and pressure measuring pipes and the static pressure and pressure measuring pipes are linearly arranged on the leading-out section, wherein the total pressure and pressure measuring pipe 8 is arranged in the middle, the first near-end static pressure and pressure measuring pipe 9 is arranged on the left side, and the three pressure measuring ends are converged into one strand of far-end static pressure and pressure measuring pipe 12 is arranged on the right side. The total temperature thermocouple 13 and the far-end temperature thermocouple 14 with three temperature measuring ends combined into one strand are linearly arranged on the leading-out section, wherein the total temperature thermocouple 13 is arranged on the left side. The two direction characteristic piezometer tubes 10 and 11 are linearly and symmetrically arranged on the leading-out section.
Under the condition of high subsonic speed incoming flow, the incoming flow is disturbed by the total/static pressure probe to form a disturbed flow field around the probe, however, the static pressure of the air flow measured by the first near-end static pressure measuring pipe 9 is actually the static pressure in the disturbed flow field of the probe, and the value is higher than the local actual static pressure of the incoming flow, namely the value is called 'position error'. The utility model discloses an embodiment, second near-end static pressure-measuring pipe 10 and third near-end static pressure-measuring pipe 11 except playing the effect of location centering, can also provide preceding body pneumatic compensation to the static pressure value that first near-end static pressure-measuring pipe 9 was measured, distal end static pressure-measuring pipe 12 can provide the pneumatic compensation of back body, therefore, four static pressure values 9 that will record, 10, 11, 12 carry out iterative operation according to certain proportional relation, can obtain the static pressure value that is more close to the actual air current that does not receive the probe vortex, this proportional relation needs to obtain in the probe calibration process fitting.
In an embodiment of the present invention, under the cross-over and supersonic incoming flow conditions, the far-end static pressure piezometer tube 12 and the far-end temperature thermocouple 13 function as: the supersonic air flow passes through the molded surface of the transition section 3 to generate a series of weak oblique shock waves, and the oblique shock waves can stop and decelerate the supersonic air flow until the supersonic speed is reduced to the subsonic speed. Because each oblique shock wave is weak, the supersonic air flow is nearly isentropically compressed through the oblique shock wave system. Therefore, the static pressure and the static temperature of the subsonic airflow on the probe horizontal rod body after the transition section are measured, and the static pressure and the static temperature of the supersonic incoming flow can be calculated, so that the accuracy of the pneumatic probe in the supersonic airflow is improved. The three detection ends are designed to be converged into a strand of outlet pipe, and the purpose is as follows: on one hand, static pressure difference and temperature difference caused by the airflow turbulence probe rod body in different directions are counteracted, and an average value is obtained and can be closer to the aerodynamic parameter of the actual airflow without disturbance; on the other hand, the sizes of the leading-out sections of the static pressure piezometer tube and the temperature thermocouple can be reduced after the probe rod bodies are converged, so that the size of the probe rod body is reduced, and the interference degree of the probe rod body on air flow is reduced. If the number of the detection ends is less than three, the above two objects cannot be achieved, and if the number of the detection ends is more than four, the probe rod body is oversized, and the flow field is seriously disturbed, so that three detection ends are preferable.
In an embodiment of the present invention, by using the present invention to provide a composite pressure-temperature probe for indirectly calculating the air velocity, the total pressure measuring tube 8 of the pressure measuring head 1 measuresAnd obtaining a total pressure value, measuring by a first near-end static pressure measuring pipe 9 of the static pressure measuring section 2 to obtain a static pressure value, and measuring by a second near-end static pressure measuring pipe 10, a third near-end static pressure measuring pipe 11 and a far-end static pressure measuring pipe 12 on the probe horizontal rod body 4 to obtain a static pressure pneumatic compensation value. The total temperature and the static temperature can be obtained through the electric signals output by the total temperature thermocouple 13 and the far-end temperature thermocouple 14 and the calibration relation. The accurate total pressure P can be obtained by integrating the data*Static pressure PsAnd a temperature value T, and calculating a speed factor according to the adiabatic exponent k
Then, the pneumatic function is obtained
Further, the gas compression factor is obtained
Then obtaining the density rho of the current ground gas flow by an ideal gas state equation ps/rho ═ RT (R is a thermodynamic constant), and finally obtaining the local speed
The utility model discloses general in measure from low-speed to supersonic speed pneumatic parameters such as total temperature, quiet temperature, total pressure, static pressure, incoming flow mach number, the velocity of flow of air current under the incoming flow condition simultaneously with the ground, can be used for wind-tunnel experiment and aircraft flight parameter's test, measurement accuracy is high, compatible strong, the commonality is good.
Compared with the prior art, the utility model discloses following beneficial effect has:
1. the total temperature thermocouple is embedded between the total pressure measuring pipe of the probe and the inner wall of the pressure measuring head part instead of being bound outside the probe rod body, so that the size of the composite probe rod body is greatly reduced, the composite probe rod body can be maintained on the same size of the traditional pressure probe, and the interference of the composite probe on a flow field is effectively reduced. Meanwhile, a temperature signal measured by the embedded total temperature thermocouple can be used as an important criterion for judging that the head of the incoming flow turbulent flow probe forms a shock wave structure, so that automatic alternation of a subsonic probe calibration algorithm and a supersonic probe calibration algorithm is realized, and the application range of the pneumatic probe is effectively widened.
2. Preferably, the semiparabolic semi-infinite length rotation body is adopted as the molded line of the probe pressure measuring head, the technology is mature, abundant experiments and numerical data support are provided, and the accurate design of the geometric dimensions of each key part of the probe is facilitated. Meanwhile, the influence of the position error of the modern aircraft nose on the probe can be equivalent to the pressure distribution of a semiparabolic semi-infinite length rotation body, so that the pneumatic compensation design scheme of the probe can be simplified.
3. The two static pressure-measuring tubes are adopted to be used as front body pneumatic compensation for static pressure measurement of the direction characteristic pressure-measuring tube and the probe, and meanwhile, the far-end static pressure tube is adopted to be used as rear body pneumatic compensation for static pressure measurement of the probe, so that the position error formed by turbulent probes flowing in the incoming flow under the condition of subsonic velocity incoming flow can be obviously weakened, the influence on the use of the whole probe after the blockage of a single static pressure-measuring tube in the actual use process can be avoided, and the measurement accuracy of the probe is improved.
4. The transition section of the regular rotating body with the variable diameter and the far-end static pressure measuring pipe arranged on the horizontal rod body of the probe can obtain a static pressure value equal to the far-end incoming flow under the conditions of crossing and supersonic incoming flow, thereby improving the use of a Pitot-Rayleigh formula
And solving the accuracy of the real total static pressure value under the conditions of cross-over and supersonic incoming flow. In addition, the remote temperature thermocouple can also be used as the pneumatic compensation of the total temperature thermocouple of the probe pressure measuring head, and the reliability of the temperature change as the criterion for generating shock waves is improved.
5. Whether the probe installed in the wind tunnel experiment is over against the incoming flow direction or not can be judged by adopting two pressure differences obtained by measuring through the direction characteristic pressure measuring pipe, the accuracy of probe installation centering is improved, and therefore the accuracy of experiment incoming flow Mach number and attack angle is effectively improved. Meanwhile, under the condition of icing or dust blockage, the problem of large total and static pressure measurement errors is reduced, and the reliability and safety of the aircraft are improved.
6. Introducing a gas compression factor on the calculation method of the incoming flow velocityThe Bernoulli equation is corrected, the accurate incoming flow speed value can be calculated only by using the pressure reading of the probe measuring hole, the application range of the method comprises the conditions of low-speed incoming flow to high-subsonic-speed incoming flow, and meanwhile, the workload of the wind tunnel calibration experiment of the probe can be reduced as much as possible.
In the above embodiments of the present invention, the terms "upper", "lower", "left", "right", and "front" are used as references with respect to the directions shown in the drawings, and these terms are used for convenience of description only and do not represent limitations on the specific technical aspects of the present invention.
While the present invention has been described in detail with reference to the preferred embodiments thereof, it should be understood that the above description should not be taken as limiting the present invention. Numerous modifications and alterations to the present invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be limited only by the attached claims.
Claims (12)
1. A composite pressure-temperature probe, comprising: the probe rod body comprises a horizontal rod body and a vertical rod body which are perpendicular to each other, the front end of the horizontal rod body is connected with a static pressure measuring section through a transition section, the static pressure measuring section is connected with a pressure measuring head, the tail end of the vertical rod body is connected with a leading-out section, and a positioning block is arranged on the side wall of the vertical rod body, which is opposite to the incoming flow direction;
the detection ends of the total pressure-measuring pipe and the total temperature thermocouple are arranged at the pressure-measuring head, the detection ends of the three near-end static pressure-measuring pipes are arranged on the side wall of the static pressure measuring section, the detection ends of the one far-end static pressure-measuring pipe and the one far-end temperature thermocouple are arranged on the side wall of the horizontal rod body, and all the pressure-measuring pipes and the thermocouples extend out of the leading-out section.
2. A composite pressure-temperature probe according to claim 1, wherein the profile of the pressure sensing head is a semiparabolic, semiinfinite-length revolution;
the expression of the rotation bus of the rotation body is as follows:
wherein the length of the rotation bus of the semiparabolic rotation body is xhLength x of revolution generatrixhThe ratio of the length to the diameter D of the pressure measuring head is called the slenderness ratio f of the probe, and the value range of the slenderness ratio f is f ═ xh3.39-5.82,/D, length x of rotary bushSatisfies x between the total length L from the pressure measuring head to the horizontal rod bodyh/L＝0.1077～0.1538。
3. A composite pressure-temperature probe according to claim 1, wherein the probing end of the total pressure piezometer tube is disposed at the tip of the piezometer head facing the incoming flow direction, and the ratio D/D between the inner diameter D of the total pressure piezometer tube and the outer diameter D of the piezometer head is 0.3-0.5.
4. A composite pressure-temperature probe according to claim 1, wherein said three proximal static pressure-measuring tubes comprise a first proximal static pressure-measuring tube, a second proximal static pressure-measuring tube and a third proximal static pressure-measuring tube, wherein the normals of the detecting ends of said three proximal static pressure-measuring tubes are aligned with the normal direction of the outer wall surface of said static pressure measuring section;
the detection end of the first near-end static pressure piezometer tube is arrangedOn the vertical downward side wall of the static pressure measuring section, the normal line of the detecting end of the first near-end static pressure measuring pipe is parallel to the central line of the vertical rod body; the center of the detection end of the first near-end static pressure piezometric tube is away from the length x of the tip of the probe headsThe following conditions are satisfied:
wherein x ishThe length of a rotary bus of a semi-parabolic semi-infinite length rotating body of the pressure measuring head is d, the inner diameter of the total pressure measuring pipe is d, and the total length from the pressure measuring head to the horizontal rod body is L;
the detection end of the second near-end static pressure-measuring pipe and the detection end of the third near-end static pressure-measuring pipe are arranged on the side wall of the upper half circumference of the static pressure measurement section, the detection end of the second near-end static pressure-measuring pipe and the detection end of the third near-end static pressure-measuring pipe are in axisymmetric distribution, and the symmetry axis is the normal line of the detection end of the first near-end static pressure-measuring pipe.
5. A composite pressure and temperature probe according to claim 4, wherein the angle between the normal to the probe end of the second proximal hydrostatic pressure tube and the normal to the probe end of the first proximal hydrostatic pressure tube is 120 °, and the angle between the normal to the probe end of the third proximal hydrostatic pressure tube and the normal to the probe end of the first proximal hydrostatic pressure tube is 120 °.
6. A composite pressure-temperature probe according to claim 1, wherein said total thermo-couple is disposed on the upper side of said total pressure piezometer tube, and the probing end of said total thermo-couple is disposed on the piezometer head through a stagnation cover.
7. A composite pressure-temperature probe according to claim 1, wherein the transition section is a section of regular rotating body with variable diameter,the diameter of one end of the transition section, which is connected with the static pressure measuring section, is smaller than that of one end of the transition section, which is connected with the horizontal rod body, the length of one end of the transition section, which is connected with the static pressure measuring section, and the tip of the probe head is 3 times of the length of the center of the detecting end of the first near-end static pressure measuring tube from the tip of the probe head, namely 3xsThe length of the transition section is equal to the length x from the center of the detection end of the first near-end static pressure measuring pipe to the tip of the probe heads。
8. A composite pressure-temperature probe according to claim 1, wherein said one distal pressure-measuring tube comprises three distal pressure-measuring tube probing ends, said three distal pressure-measuring tube probing ends being uniformly distributed on the side wall of the horizontal rod body; the strand of far-end temperature thermocouple comprises three far-end temperature thermocouple detection ends, and the three far-end temperature thermocouple detection ends are uniformly distributed on the side wall of the horizontal rod body; the detection end of the far-end static pressure piezometer tube and the detection end of the far-end temperature thermocouple are arranged at intervals; the length from the center of the detection end of the far-end static pressure piezometer tube to the tip of the probe head is xcThe length of the center of the detection end of the remote temperature thermocouple from the tip of the probe head is xcL is the total length of the pressure measuring head to the horizontal rod body, 0.70L.
9. A composite pressure and temperature probe according to claim 8, wherein the normal of each of said distal pressure and pressure tubes is aligned with the normal of the outer wall of the horizontal shaft, the angle between the normals of two adjacent distal pressure and pressure tubes is 120 °, and one of said distal pressure and pressure tubes is disposed on the vertically downward wall of said horizontal shaft.
10. A composite pressure-temperature probe according to claim 8, wherein each of the remote temperature thermocouple probe tips is disposed on the side wall of the horizontal shaft through a stagnation cover, the normal line of each of the remote temperature thermocouple probe tips is aligned with the normal line of the outer wall surface of the horizontal shaft, the angle between the normal lines of two adjacent remote temperature thermocouple probe tips is 120 °, and one of the remote temperature thermocouple probe tips is disposed on the vertically upward side wall of the horizontal shaft.
11. The composite pressure-temperature probe of claim 1, wherein the positioning block is a groove formed in the vertical rod, the positioning block has a depth of 30% or less of the wall thickness of the vertical rod, and the surface normal direction of the positioning block faces the incoming flow direction.
12. A composite pressure-temperature probe according to claim 4, wherein said total pressure piezometric tube, said first proximal static pressure piezometric tube and said distal static pressure piezometric tube are linearly arranged on said lead-out section, said total pressure piezometric tube being disposed in the middle; the total temperature thermocouple and the strand of far-end temperature thermocouple are linearly arranged on the leading-out section; the second near-end static pressure piezometer tube and the third near-end static pressure piezometer tube are linearly arranged on the leading-out section; the total pressure-measuring pipe, the first near-end static pressure-measuring pipe and the strand of far-end static pressure-measuring pipe are arranged in the middle.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113916486A (en) * | 2021-10-11 | 2022-01-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel rapid pressure measurement and control method based on multi-parameter pressure regression algorithm |
| CN114088971A (en) * | 2022-01-21 | 2022-02-25 | 中国空气动力研究与发展中心空天技术研究所 | Waterproof wind speed measuring device |
| CN114233671A (en) * | 2021-12-21 | 2022-03-25 | 中国科学院工程热物理研究所 | Performance test method for supercritical carbon dioxide centrifugal compressor |
| CN114427974A (en) * | 2022-01-27 | 2022-05-03 | 中国航发沈阳发动机研究所 | Integrated probe |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113916486A (en) * | 2021-10-11 | 2022-01-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel rapid pressure measurement and control method based on multi-parameter pressure regression algorithm |
| CN114233671A (en) * | 2021-12-21 | 2022-03-25 | 中国科学院工程热物理研究所 | Performance test method for supercritical carbon dioxide centrifugal compressor |
| CN114233671B (en) * | 2021-12-21 | 2024-05-03 | 中国科学院工程热物理研究所 | Performance test method for supercritical carbon dioxide centrifugal compressor |
| CN114088971A (en) * | 2022-01-21 | 2022-02-25 | 中国空气动力研究与发展中心空天技术研究所 | Waterproof wind speed measuring device |
| CN114427974A (en) * | 2022-01-27 | 2022-05-03 | 中国航发沈阳发动机研究所 | Integrated probe |
| CN114427974B (en) * | 2022-01-27 | 2023-11-28 | 中国航发沈阳发动机研究所 | Integrated probe |
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